Adjustable ring

ABSTRACT

A charging device adjusting ring for a variable turbine and/or compressor geometry is disclosed. The charging device may include at least one inwardly directed recess for receiving at least one blade lever heads of a blade lever, wherein each recess comprises at least two lateral flanks. Additionally, at least one of the at least two flanks has a curved shape, and wherein the at least two flanks have a predefined deviation from a parallel arrangement.

CROSS-REFERENCES TO RELATED APPLICATION

This application claims priority to German patent application 10 2011005 556.8 filed on Mar. 15, 2011, which is hereby incorporated byreference in its entirety.

TECHNICAL FIELD

The disclosure relates to an adjusting ring for a variable turbineand/or compressor geometry. The disclosure additionally relates to avariable turbine and/or compressor geometry with such an adjusting ring.Furthermore, the disclosure relates to a charging device, in particularan exhaust gas turbocharger, having a variable turbine and/or compressorgeometry of the mentioned type.

BACKGROUND

The variable turbine and/or compressor geometry is an establishedtechnique for the power control of a charging device, in particular ofan exhaust gas turbocharger, with different gas throughputs. Therefore,an adjusting ring with recesses is provided, which substantially showtwo parallel lateral flanks, wherein the recesses receive blade leverheads of blade levers. In the process, the blade lever heads are movedthrough a contact with the flanks of the recesses of the adjusting ring,which results in a rotation of guide blades arranged on a blade bearingring, which are connected to the blade levers in a rotationally fixedmanner via a blade mounting pin. Here, the cross section opened by theguide blades is reduced upon high power demand through the chargingdevice and/or low propulsion gas throughput. Accordingly, the crosssection that is available through the guide blades is increased upon lowpower demand through the charging device and/or high drive gasthroughput. Disadvantageous in this case is that a gap between the bladelever heads and the corresponding flank can develop, which results in asluggishness of the variable turbine and/or compressor geometry.Furthermore, an incorrect transmission of an adjusting force via theflanks to the corresponding blade lever heads for the development of afriction takes place, which likewise contributes to the sluggishness ofthe variable turbine and/or compressor geometry. The sluggishness, inparticular with load changes or changes of the power demand by thecharging device, leads to a delayed reaction time or a hysteresis andthus a power reduction of the charging device.

Generic adjusting rings are known for example from DE 10 2007 022 356 A1and DE 10 2004 023 209 A1.

SUMMARY

The present disclosure therefore deals with the problem of stating animproved embodiment for an adjusting ring of the generic type, which inparticular contributes to an elimination or at least reduction of thehysteresis behaviour of the variable turbine and/or compressor geometry.

According to the disclosure, this problem is solved through the featuresof the independent claims. Advantageous embodiments are the subject ofthe dependent claims.

The present disclosure is based on the general idea of configuring theflanks of at least one recess with an adjusting ring of a variableturbine and/or compressor geometry of a charging device, wherein theadjusting ring comprises recesses directed to the inside for mountingblade lever heads of blade levers and each mount comprises two flanks,in such a manner that the blade lever heads and at least one of theflanks of the associated recesses have a contact for any positions ofthe associated guide blade and thus of the blade lever heads. Inaddition or alternatively, the flanks are designed in such a manner thata transmission of an adjusting force via the flanks to the correspondingblade lever heads is optimised. The disclosure thereby utilises therealisation that a gap between a blade lever head and the flank of theassociated clearance of the adjusting ring is caused through theparallel arrangement of the flanks of a recess with certain positions ofthe adjusting ring and thus of the blade lever heads. A friction causedthrough an unfavourable transmission of the adjusting force betweenblade lever head and flank is in particular caused through the parallelarrangement of the flanks as well, which make possible an optimaltransmission of the adjusting force only with certain adjustingpositions of the adjusting ring and thus with certain positions of theblade lever head. Corresponding to the general inventive idea, at leastone flank of at least one recess has a curved shape, in particular aparabolic shape, or both flanks of a recess have a predefined deviationfrom a parallel arrangement. The curvature angle of the for examplecurved flanks can in particular have a dependency on a nominal diameterof the blade lever head. The curved shape of the flank in this caseserves in particular for the purpose of guaranteeing a contact betweenblade lever head and said flank for any positions of the guide bladesand thus of the blade lever head. In addition or alternatively, theseembodiments of the flank serve for the purpose of optimising anadjusting force transmitted by the flank onto the blade lever head insuch a manner that the friction between flank and blade lever head is atleast reduced.

With an alternative embodiment, the flanks of a recess are designed insuch a manner that they have a predefined deviation from a parallelarrangement. Accordingly, the flanks are configured in such a mannerthat they are for example arranged obliquely to one another. Such anarrangement, too, serves in particular for the purpose of guaranteeing acontact between blade lever head and the corresponding flank/flanks forany positions of the guide blades and thus of the blade lever head. Inaddition or alternatively, this embodiment of the flanks serves for thepurpose of optimising an adjusting force transmitted to the blade leverhead through the flank in such a manner that the friction between flankand blade lever head is at least minimised.

With a further embodiment of the solution according to the disclosure,the flanks of a recess, which have a deviation from a parallelarrangement, are designed in such a manner that at least one of theflanks runs in a radial plane of the adjusting ring. Alternatively, bothflanks of a recess can also lie in a radial plane. This arrangement ofthe flanks now leads in particular to the contact between blade leverhead and flank/flanks for any positions of the guide blades and thus ofthe blade lever head being guaranteed. Here, too, the force transmissioncan be improved, the hysteresis effect and the friction reduced.

A further advantageous embodiment comprises flanks of at least onerecess, which are arranged in mirror image to one another. As anexample, reference is made here to flanks which are mirrored to oneanother with respect to a radial plane of the adjusting ring running intheir middle. The flanks are thus designed in particular with curvedshape of the respective flanks in such a manner that the make availablethe same, however mirrored, mount on both sides of the associatedrecess.

With a further embodiment, a base of the recess additionally to thealready mentioned embodiments has a curved shape. Here, the base can befor example rounded off in order to prevent in particular a friction ofthe blade lever head with the base of the associated recess.

According to an advantageous further development, the adjusting ring isintegrated in a variable turbine and/or compressor geometry. Here, theblade levers are connected by blade lever pins to a blade bearing ring,wherein guide blades are coupled to the blade lever pins in arotationally fixed manner. This further development now serves inparticular for the purpose of at least reducing a friction force betweenthe flanks of the recesses of the adjusting ring and the associatedrecesses, independently of the position of the blade bearing ring andthus of the associated guide blades.

According to an advantageous embodiment of the variable turbine and/orcompressor geometry according to the disclosure, the flanks of theadjusting ring are designed in such a manner that the associated bladelever heads are supported substantially orthogonally on the associatedflank independently of the position of the adjusting ring and thus ofthe guide blades. This orthogonal support in this case serves inparticular for the purpose of achieving an optimal transmission of theadjusting force to the blade lever heads and thus to the guide bladesthrough the adjusting ring.

It is pointed out that the rotation of the adjusting ring in a variableturbine and/or compressor geometry merely runs over a few angulardegrees. Accordingly, the respective flanks according to the disclosurecan be designed in such a manner that they merely ensure an optimisedtransmission of the adjusting force between adjusting ring and bladelever head and/or a contact between blade lever head and the associatedflank merely in the relevant angular range.

Further important features and advantages of the disclosure are obtainedfrom the subclaims, from the drawings and from the associated Figuredescription by means of the drawings.

It is to be understood that the features mentioned above and still to beexplained in the following cannot only be used in the respectivecombination stated but also in other combinations or by themselveswithout leaving the scope of the present disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

Preferred exemplary embodiments of the disclosure are shown in thedrawings and are explained in more detail in the following description,wherein same reference numbers refer to same or similar of functionallysame components.

It shows, in each case schematically:

FIG. 1-4 in each case a detail of an adjusting ring according to thedisclosure.

DETAILED DESCRIPTION OF THE DRAWINGS

As is shown in FIG. 1 to FIG. 4, an adjusting ring 1 comprises at leastone recess 2, wherein the recesses 2 comprise two lateral flanks 3, 3′and a base 4.

In the embodiment of the adjusting ring 1 according to the disclosureshown in FIG. 1, both flanks 3, 3′ of the shown recess 2 have a curvedshape, wherein both flanks 3, 3′ show an angular transition to theadjusting ring 1. Of course, this can also be round shaped. Here, one ofthe flanks 3 corresponds to the mirror image of the other flank 3′ withrespect to a mirror plane 5 running in the middle of both flanks 3, 3′,which forms a radial plane of the adjusting ring 1 at the same time. Thebase 4 of the recess 2 likewise has a curved shape, wherein thecurvature angle of the flanks 3, 3′ and of the base 4 differ in that thebase 4 has a greater curvature.

With a corresponding design of the flanks 3, 3′ according to FIG. 1, afixing of the respective blade lever head in radial direction in theassociated recess 2 can also take place.

FIG. 2 shows an alternative embodiment of the flanks 3, 3′ of the recess2 having an angular transition to the adjusting ring 1. The flanks 3, 3′in this case are flat and have a predefined deviation from a parallelarrangement in such a manner that they exhibit an inclination to oneanother and contact one another in an acute base 4. The flanks 3, 3′ arefurthermore designed in such a way that one of the flanks 3 correspondsto the mirror image of the other flank 3′ with respect to the mirrorplane 5 running in the middle of both flanks 3.

FIG. 3 show a further embodiment of an adjusting ring 1 according to thedisclosure, whose recess 2 comprises a flat flank 3 and a curved flank3′, wherein both flanks 3, 3′ have an angular transition to theadjusting ring. The curved flank 3′ in this case touches the flat flankin the base 4 of the recess 2, by which a curved base 4 of the recess 2is formed.

In the embodiment of the recess 2 of an adjusting ring 1 shown in FIG.4, the transition between the adjusting ring 1 and the recess 2 isrounded off. Here, the transition to a flank 3 has a different roundingthan the transition to the other flank 3′. The flanks 3, 3′ in this caseare each flat, while they deviate from a parallel arrangement in such amanner that they lie on radial planes 6 which pass through the centrepoint 7 of the adjusting ring 1. The flat flanks 3, 3′, which lie on theplanes 6, meet in a curved and rounded-off base 4 of the associatedrecess 2. The flanks 3, 3′ are embodied furthermore in such a mannerthat one of the flanks 3′ corresponds to the mirror image of the otherflank 3 with respect to a mirror plane 5 running in the middle of bothflanks 3, 3′.

These embodiments in particular serve for the purpose of improving atransmission of an adjusting force via the flanks 3, 3′ to theassociated blade lever heads through the shape of the flanks 3, 3′. Thisis effected in particular in that the flanks 3, 3′ are designed suchthat their shape and arrangement ensure a substantially orthogonalsupport of the associated blade lever head, independently of theposition of the corresponding guide blades and thus of the blade leverhead. The force introduction between the lever head and the adjustingring 1 merely takes place in circumferential direction (tangentially) ofthe adjusting ring 1.

1. A charging device adjusting ring for a variable turbine and/orcompressor geometry, comprising: at least one inwardly directed recessesfor receiving at least one blade lever heads of a blade lever, whereineach recess comprises at least two lateral flanks, wherein at least oneof the at least two flanks has a curved shape, and wherein the at leasttwo flanks have a predefined deviation from a parallel arrangement. 2.The adjusting ring according to claim 1, wherein at least one of the atleast two flanks is configured to extend in a radial plane of theadjusting ring.
 3. The adjusting ring according to claim 1, wherein theat least two lateral flanks are configured in a mirror image manner withrespect to each other.
 4. The adjusting ring according to claim 1,wherein a base of one of the recesses has a curved shape.
 5. A variableturbine or compressor geometry, comprising: a blade bearing ring, inwhich at least one guide blade is rotatably mounted via a correspondingblade bearing pin; and an adjusting ring configured with at least twoflanks having a predefined deviation from a parallel configuration. 6.The variable turbine or compressor geometry according to claim 5,wherein at least one of the at least two flanks is configured such thatthe blade lever head supports itself substantially orthogonally on theat least one at least two flank independently of the position of theguide plates.
 7. The variable turbine or compressor geometry accordingto claim 5, wherein an area is configured between the blade lever headand the adjusting ring to receive a force in a circumferential direction(tangentially) of the adjusting ring.
 8. An exhaust gas turbo chargingdevice, having a variable turbine or compressor geometry, comprising: ablade bearing ring; at least one guide blade a blade bearing pinconfigured to rotatably mount each at least one guide blade to the bladebearing ring; and an adjusting ring configured with at least two flankshaving a predefined deviation from a parallel configuration.
 9. Theadjusting ring according to claim 1, wherein a shape of the at least oneof the at least two flanks is configured as a parabolic.
 10. Theadjusting ring according to claim 5, wherein at least one of the atleast two flanks is configured to extend in a radial plane of theadjusting ring.
 11. The adjusting ring according to claim 5, wherein theat least two lateral flanks are in a mirror image configuration withrespect to each other.
 12. The adjusting ring according to claim 5,wherein a base of one of the recesses has a curved shape.
 13. Theadjusting ring according to claim 8, wherein at least one of the atleast two flanks is configured to extend in a radial plane of theadjusting ring.
 14. The adjusting ring according to claim 8, wherein theat least two lateral flanks are configured in a mirror image manner withrespect to each other.
 15. The adjusting ring according to claim 8,wherein a base of one of the recesses has a curved shape.